Airplane



sept. 27, v1943.2.

C. B'. HARPER Film1` April 5. 11922 AIRPLAN.r

1sA sheds-sheet 1 Sept Z7, l932- c. B. HARPER 1,880,019

` l AIRPLANE Filed April 3f 1922 19 Sheets-Sheet 2 Sept. V27, 1932. c'. B. HARPER 1,880,019

AIRPLANE Filed April 3 1922 19Sheets-Sheetv3 SHR.: nel;

19 'sheets-sheet 4 sept. 27, 1932.

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c. B. .HARPER AIRPLANE Filed April 3. 1922 lSShBebS-Sheet 5 Sept.'27, 1932. c. B. HARPER 1,880,019

AIRPLANE Filed April s. 1922 19sheetssheet 6 Sept. 27, 1932. A c. B. HARPER 1,880,019

' AIRPLANE Filed April 3. 1922 ISShSe'S-Sheeb 7 v Sept. 27, 1932. c. B. HARPER 1,830,019

AIRPLANE Filed April 3. 1922 19 Sheets-Sheet 8 Sept. 27, 1932.

C. B. HARPER AIRPLANE Filed April 3. 1922 19 Sheets-Sheet 9 Sept 27, 1932- c. B. HARPER 1,880,019

` AIRPLANE l Filed April 3. 1922 v 19 sheets-sheet 1o Sept. 27, 1932. c. B. HARPER AIRPLANE Filed April 3. 1922 19sheetssheet- 11 Sept. 27,193.2.l g, B, HARPER f 1,880,019

AIRPLANE `Filed April 5. 1922 19 Sheets-sheet l2 SePt 27, 1932. c. HARPER I l1,880,019

AIRPLANE FiledfAPll 3. 1922 19.511ee'cs-Shee1'I 13 affanni/4.

Sept. A27, 1932. c. B. HARPER AIRPLANE Filed April 5 1922 v 19 Sheets-sheet 14 Sept. 27, 1932. I c. B. HARPER 1,880,019

AIRPLANE Filed April s. 1922. 19 shams-smetV 15 Sept.V 27, 1932. c. B. HARPR AIRPLANE Filed'Aprl 3, 1922 19 Sheets-Sheet 16 atienda SePt- 27,1932. f c. B. HAPER 1,880,019

/ Filed April 3. 1922 1'9 sheetsfseet 17' u "eBQlBHar/oer Sept.27, I1932. d. B. HARPER AIRPLANE Filed April v5. 1,922 -.19 sheets-sheet 1sl Sept. 27, 1932. c.v B. HARPER' AIRPLANE Filed April 5. A1922 19vSheets-Sheet 19 abbina# Patented Sept, 27, 1932 unirse srarss PATENT OFFICE AIBPLANE Application led April 3, 1922. Serial No. 549,225.

This invention relates to improvements in airplanes and more particularly to the Hight control mechanism.

One of the objects of the present invention is to provide an improved airplane construction which will change the aerodynamic characteristics of the aerofoil for the purpose of increasing the s eed range,climb and celllng.

A further object is to provide an improved aerofoil with trailing edge iiap for the purpose of increasing the speedrange of the airplane.

" A further object is to provide an aerofoil that will enable the plane to land or take-off i 5 with greater facility.

A further object is to provide an aerofoll ""--on the side of the airplane it is desired -tobe lowered. V Other objects will be in part obvious and in part hereinafter pointedout in connection trate in detail one of 4the various possible Amodifications of the Vstructure as ,WelLas various modifications in diagrammatic form showing various types of spoilers applicable to wing sections designedto have a change 0 lof Camber.

In these drawings similar reference characters denote corresponding parts throughout the several views So far as possible and wherein Figurel is a diagrammatic side elevational view of a plane having the near wing omitted and certain parts broken awav to show the l0- cation of the interior control mechanism more clearly.

Figure 2 is a transverse sectional view taken substantially on the line 2-2 of Figure 1. i Figure 3 is a plan view of a part of one of the wings.

Figures 4 and 4a together constitute an enlarged detail section through the wing at a point termed as a main rib section. Figures 5, 6 and 7 arev detail views of certain parts shown in Fi re 4. Figures 8 and 8a together illustrate an enlarged detail sectional view of a typical n section through the wing intermediate the main wing sections.

Figure 9 is a' fragmentary plan view of Acertain parts shown in Figure 8.

Figure 10 is a typical cross section through '65 a main rib.

Figures 11 to 16a, inclusive, show slightly modified forms of spoilers or flaps used for lateral control.

Figure 17 shows arigid type of vstabilizer 70 provided with a swelling lower surface. Figure 18 shows a rigld type of stabilizer with the swelling feature omitted but having spoilers.

Figures 19 to 22, inclusive, show details 75' of a type of control especially designed for operating' spoilers or iapsas shown in. Figure 16.

Figure23 is a. detail view showing -a de- Velopment of a cam bell crank lever illusv tra-ted in Figures '2O and 21.

Figure 24 is an enlarged detail Iview* of certain control parts shown in Figure'l. with the accompanying drawings which'illus- -The general arrangement -and constructior. of my invention'con'sists in the use ofa 85 Hap lor spoiler locatedl on the upper' surface of thewing and nearthe n os'e thereof `operable from the cockpit in conjunction with means for varying the normal lift vof the ^i wing or wings such as swelling the wing or otherwise varying the normal airflow over the surface thereof. This construction may be used complementary to 'or in place of the usual control now employed on aircraft. v v

Trailing edge flaps, which 'further' control the lift of the wing may be operated in conjunction with the operation of the spoilers, which flaps may be operated either simultaneously or separately. Likewise they may be operated simultaneously with the means for 

